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OrigamiSat 1

OrigamiSat 1 [TITech]

The OrigamiSat 1 (ORganizatIon of research Group on Advanced deployable Membrane structures for Innovative space science Satellite)is a 3U CubeSat designed at Tokyo Institute of Technology (TITech) to demonstrate an advanced membrane space structure in orbit.

The objectives of the OrigamiSat 1 missions are:

  • Membrane deployment mission: To contribute to the realization of future applications, an highly functional membrane structure is deployed, and its deployment behavior and deployed shapes are measured in orbit.
  • Space-demonstration scheme development mission: To obtain space-demonstration scheme for researchers of space deployable structures, commercially available components are used or developed.
  • Amateur radio mission: To enhance radio communication skills, 5.84 GHz high-speed transmission from space is used

The Origamisat system consists of four major subsystems: bus, membrane deployment system, extendable camera system, and ground station. For the bus, most components are composed of commercial off-the-shelf (COTS) components. This design aims at facilitating the future space demonstration of advanced space deployable structures by university/company researchers. The membrane deployment system deploys a membraneboom integrated structure. Its membrane folding pattern, called rotationally skew folding, enables the attachment of thin-film devices on the membrane, such as thin-film solar cells and thin SMA antennas. The deployable camera system takes pictures of the deployed membrane on orbit. It has an approximately 1 m length deployable mast, and the camera is installed on the tip of the deployable mast.

The CubeSat will be launched into a 230 km perigee and 630 km apogee orbit with 97.4 deg.

The satellite will be launched as a secondary payload from Japan in Jan 2018 together with AOBA-VELOX 4.

Nation: Japan
Type / Application: Technology
Operator: Tokyo Institute of Technology (TITech)
Contractors: Tokyo Institute of Technology (TITech)
Equipment:
Configuration: CubeSat (3U)
Propulsion:
Power: Solar cells, batteries
Lifetime:
Mass: 4 kg
Orbit: 230 km × 630 km, 97.4
Satellite COSPAR Date LS Launch Vehicle Remarks
OrigamiSat 1 - 2018 Ka LP-M Epsilon-2 CLPS with Innovative technology demonstration satellite 1, Hodoyoshi 2, AOBA-VELOX 4

References: